CN107487434B - Fixed wing aircraft cockpit - Google Patents
Fixed wing aircraft cockpit Download PDFInfo
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- CN107487434B CN107487434B CN201710645316.XA CN201710645316A CN107487434B CN 107487434 B CN107487434 B CN 107487434B CN 201710645316 A CN201710645316 A CN 201710645316A CN 107487434 B CN107487434 B CN 107487434B
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- cockpit
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- aircraft
- wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
- B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Emergency Lowering Means (AREA)
- Window Of Vehicle (AREA)
Abstract
The invention relates to the structural design of an aircraft cockpit, in particular to a fixed-wing aircraft cockpit. A fixed-wing aircraft cockpit, comprising: the mounting opening is formed in the cockpit and right above the driver seat; the shape and the size of the mounting port frame are matched with those of the mounting port, and the mounting port frame is detachably and fixedly arranged in the mounting port; the shape and the size of the emergency escape window are matched with the mounting opening frame and are fixedly arranged in the mounting opening frame. According to the fixed-wing aircraft cockpit, the emergency escape window is detachably arranged right above the cockpit seat in the cockpit, so that on one hand, the seat can be used for quickly climbing out of an escape exit for escape, the time required by emergency evacuation of fixed-wing aircraft pilots is greatly shortened, the design difficulty can be reduced, and the requirement on the internal space of an aircraft is reduced; on the other hand, when the engine is in a parking state, the escape window is opened, and the problem of ventilation of the cockpit can be solved.
Description
Technical Field
The invention relates to the structural design of an aircraft cockpit, in particular to a fixed-wing aircraft cockpit.
Background
At present, the emergency escape exit of a fixed-wing aircraft pilot is generally arranged at the top of the rear section of a cockpit or at two sides of a fuselage. When the engine is stopped, the ground of the cockpit is ventilated by the ventilation window arranged on the outermost side of the windshield.
For the emergency exit arranged at the top of the rear section of the cockpit, a driver needs to quickly arrive at the emergency exit area when evacuating, open the emergency exit, climb out of the emergency exit by means of emergency evacuation auxiliary facilities such as an escape ladder and the like, and accordingly evacuate. On one hand, the emergency exit needs to be provided with an emergency evacuation auxiliary facility, the design is complex, and the occupied space in the fuselage is large; on the other hand, when the driver evacuates, the evacuation route is long, the operation flow is complex, the time is long, and the rapid evacuation is not facilitated.
For emergency exits arranged on both sides of the fuselage, an unobstructed rectangular exit of a given size must be included, occupying a relatively large space inside the fuselage. In addition, the outlet is required to be arranged above a waterline on the side surface of the airplane, so that the outlet is convenient to use when the airplane is forced to land on water, and the design of the outlet is difficult for the airplane with a smaller fuselage diameter.
For a ship-based fixed wing aircraft adopting a compact layout form to meet the requirement of suitability of a ship, in order to solve the problem of ventilation of a cockpit when engines in a shutdown state, such as an in-and-out parking space, a lifter, a dispatching and transportation in an aircraft warehouse and the like, a ventilation window must be arranged, an opening device is designed, an extra opening space is reserved, and the difficulty is high.
In addition, for the planes needing formation flying, such as carrier-borne fixed-wing early warning planes, maritime patrol anti-dive planes and the like, the observation of the position of a wing plane is mainly realized through flat display, the wing plane at the opposite side can also be observed through a side observation window, but a complementary more intuitive observation method is lacked for the wing plane above.
Disclosure of Invention
The invention aims to provide a fixed-wing aircraft cockpit, which solves at least one problem existing in the conventional cockpit in use.
The technical scheme of the invention is as follows:
a fixed-wing aircraft cockpit, comprising:
the mounting opening is formed in the cockpit and right above the driver seat;
the shape and the size of the mounting port frame are matched with those of the mounting port, and the mounting port frame is detachably and fixedly arranged in the mounting port;
the emergency escape window is matched with the mounting opening frame in shape and size and is fixedly arranged in the mounting opening frame.
Optionally, the fixed-wing aircraft cockpit further includes:
the installation partition plate is fixedly arranged on the inner side of a cockpit top plate right above the seat, the plate surface of the installation partition plate is perpendicular to the cockpit top plate, the installation partition plate is respectively positioned on the left side and the right side of the aircraft course direction, and the left side wall plate and the right side wall plate of the installation opening frame in the aircraft course direction are respectively and fixedly connected with the installation partition plate on the corresponding side;
the two sliding rails are symmetrically arranged on the opposite side surfaces of the installation partition plates on the left side and the right side, and the height of the front ends of the sliding rails in the aircraft course direction is greater than that of the rear ends of the sliding rails;
the two joints are respectively matched with the slide rails, each joint is arranged in one slide rail in a sliding manner, and the two joints are respectively and fixedly connected to the bottoms of the front ends of the mounting port frames on the corresponding sides in the aircraft course direction;
the two locking handles are symmetrically and rotatably arranged on the opposite side surfaces of the mounting partition plate on the left side and the right side, the rotating axes of the two locking handles are perpendicular to the plate surface of the mounting partition plate, and when the locking handle on each side rotates to a preset angle, the locking handle can be clamped with the end part of the sliding rail on the corresponding side at the rear end of the aircraft in the course direction;
operating handle is shaft-like, follows the perpendicular to installation baffle face direction rotates to set up installation mouthful frame bottom, operating handle's axis of rotation perpendicular to installation baffle face, and, operating handle's both ends respectively with correspond the side lock dead handle fixed connection for rotate through self and drive the lock dead handle rotates.
Optionally, the installation partition plate is further arranged at the front end of the aircraft in the aircraft course direction and is fixedly connected with a front end wall plate of the installation port frame in the aircraft course direction;
the emergency escape window is made of transparent glass;
the fixed-wing aircraft cockpit further includes:
and the reflector is arranged on the mounting partition plate at the front end and used for observing the environment at the top of the cockpit through the emergency escape window.
Optionally, the fixed-wing aircraft cockpit further includes:
and the mounting seat is used for fixedly mounting the reflector on the mounting partition plate and adjusting the observation angle of the reflector.
The invention has the following effects:
according to the fixed-wing aircraft cockpit, the emergency escape window is detachably arranged right above the cockpit seat in the cockpit, so that on one hand, the seat can be used for quickly climbing out of an escape exit for escape, the time required by emergency evacuation of fixed-wing aircraft pilots is greatly shortened, the design difficulty can be reduced, and the requirement on the internal space of an aircraft is reduced; on the other hand, when the engine is in a parking state, the escape window is opened, and the problem of ventilation of the cockpit can be solved.
Drawings
FIG. 1 is a schematic view of the external configuration of a fixed-wing aircraft cockpit according to the present invention;
FIG. 2 is a schematic structural view of an escape window portion of a fixed-wing aircraft cockpit for one of emergency views according to the present invention;
fig. 3 is a schematic structural view of an escape window portion of a fixed-wing aircraft cockpit for another perspective of emergency in accordance with the present invention.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
The fixed-wing aircraft cockpit of the present invention is described in further detail below with reference to fig. 1-3.
The invention provides a fixed-wing aircraft cockpit, which comprises a mounting opening 1, a mounting opening frame 21 and an emergency escape window 22.
The mounting port 1 is arranged right above a driver seat in the cockpit and penetrates through a top wall plate and a skin of the cockpit; wherein, the mounting openings 1 can be arranged right above the left driver seat and the right driver seat.
The shape and the size of the mounting port frame 21 are matched with those of the mounting port 1, and the mounting port frame is detachably and fixedly arranged in the mounting port 1. The mount frame 21 may be selected from a variety of known suitable structures as needed to better fix the emergency escape window 22. In addition, the mounting port frame 21 and the mounting port 1 can be detachably and fixedly connected in a plurality of suitable ways, for example, rubber is arranged on the contact surface around the mounting port frame 21 to realize detachable fixation, and the specific structure is not described again.
The shape and size of the emergency escape window 22 are matched with those of the mounting opening frame 21 and are fixedly arranged in the mounting opening frame 21.
According to the fixed-wing aircraft cockpit, the emergency escape window 22 is detachably arranged right above the cockpit seat in the cockpit, so that on one hand, the seat can be used for quickly climbing out of an escape exit for escape, the time required by emergency evacuation of fixed-wing aircraft pilots is greatly shortened, the design difficulty can be reduced, and the requirement on the internal space of an aircraft is reduced; on the other hand, when the engine is in a parking state, the emergency escape window 22 is opened, and the problem of ventilation of the cockpit can be solved.
The fixed-wing aircraft cockpit of the present invention may also include a mounting bulkhead 3, a slide rail 41, a dead-lock handle 43, and an operating handle 44.
The number of the installation partitions 3 may be any number; in this embodiment, the number of the partition plates 3 to be mounted is preferably three.
The two installation partition plates 3 are fixed on the inner side of a cockpit top plate right above the seat in a bolt, welding and other modes, the plate surfaces of the installation partition plates 3 are perpendicular to the cockpit top plate, the installation partition plates 3 are respectively positioned on the left side and the right side of the aircraft course direction, and the left side wall plate and the right side wall plate of the installation opening frame 21 in the aircraft course direction are respectively fixedly connected with the installation partition plates 3 on the corresponding sides.
The other installation clapboard 3 is fixed at the front end of the aircraft course direction by bolts, welding and the like and is fixedly connected with the front end wall plate of the installation port frame 21 in the aircraft course direction.
The number of the slide rails 41 is two, the slide rails 41 are symmetrically arranged on the opposite side surfaces of the installation partition plates 3 on the left side and the right side in a bolt, welding mode and the like, and the height of the front ends of the slide rails 41 in the aircraft course direction is greater than that of the rear ends.
The number of the joints 42 is two, the joints are respectively matched with the slide rails 41 on the corresponding side, each joint 42 is arranged in one slide rail 41 on the corresponding side in a sliding manner, and the two joints 42 are respectively fixedly connected to the bottom of the front end of the mounting port frame 21 on the corresponding side in the aircraft heading direction in a bolt, welding and other manners. Specifically, the joint 42 is arranged in the sliding rail 41 at the bottom, and is fixedly connected with the mounting opening frame 21 at the top.
The number of the locking handles 43 is two, the two locking handles are symmetrically and rotatably arranged on the opposite side surfaces of the mounting partition plates 3 at the left side and the right side, and the rotating axes of the two locking handles are vertical to the plate surfaces of the mounting partition plates 3; and when the locking handle 43 on each side rotates to a preset angle, the locking handle can be locked with the rear end part of the slide rail 41 on the corresponding side in the aircraft heading direction. The dead lock handle 43 can be rotatably disposed on the mounting partition 3 in various suitable manners, and in this embodiment, is preferably hinged and fixed by bolts. In addition, the dead lock handle 43 can be configured in various suitable structures as required, for example, one end of the dead lock handle 43 is configured in a C-shaped bayonet shape, and when the dead lock handle is rotated to a predetermined angle, the bayonet is just fixedly clamped at the rear end of the slide rail 41. It should be noted that the predetermined angle may be appropriately selected according to the shape and the setting position of the locking handle 43, and details thereof are not described herein.
The operating handle 44 is in a rod shape and is rotationally arranged at the bottom of the mounting opening frame 21 along the direction vertical to the plate surface of the mounting clapboard 3, and the rotating axis of the operating handle 44 is vertical to the plate surface of the mounting clapboard 3; and, both ends of the operating handle 44 are respectively and fixedly connected with the dead-lock handle 43 at the corresponding side, and are used for driving the dead-lock handle 43 to rotate through self-rotation. Specifically, the end of the operating handle 44 is hinged to one end of the dead-lock handle 43, i.e. the other end opposite to the bayonet, so that when the operating handle 44 is rotated, the end thereof can drive one end of the dead-lock handle 43, so that the other end (bayonet end) of the dead-lock handle 43 rotates around the hinge point of the dead-lock handle 43 on the installation partition 3.
In the fixed-wing aircraft cockpit of the present invention, the emergency escape window 22 may be selected as various suitable materials as required; in this embodiment, the emergency escape window 22 is preferably made of transparent glass. Further, the fixed-wing aircraft cockpit of the invention also comprises a reflector 5; the reflector 5 is arranged on the mounting partition plate 3 at the front end and used for observing the environment at the top of the cockpit through the emergency escape window through the reflector.
Further, the fixed-wing aircraft cockpit also comprises a mounting seat used for fixedly mounting the reflector 5 on the partition plate 3 and adjusting the observation angle of the reflector 5. The mounting seat can be selected from known and various suitable structures according to requirements, and details are not described here.
According to the fixed-wing aircraft cockpit, the emergency escape window 22 is a transparent window arranged at the top of the head of a pilot, when the pilot evacuates in an emergency, the pilot rotates the operating handle 44 to unlock the locking handle 43, and then pulls the operating handle 44 downwards to enable the mounting port frame 21 to slide backwards along the sliding rail 41, so that an emergency escape exit is opened, the seat can be used for climbing out of the escape exit to escape, the time required by the pilot of the fixed-wing aircraft for emergency evacuation is greatly shortened, the design difficulty is reduced, and the requirement on the internal space of the aircraft is reduced. In addition, when the fixed-wing aircraft engine is in a parking state, the emergency escape exit is opened, and the problem of ventilation of the cockpit can be solved. Furthermore, the escape exit is provided with a reflector 5 with adjustable angle which is arranged on the clapboard 3, so that a plurality of machines can be used for observing the wing plane above the escape exit when the machines form a formation flight. The invention can be widely applied to various fixed-wing aircrafts, including carrier-borne fixed-wing early warning aircrafts, maritime patrol anti-diving aircrafts and the like.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (3)
1. A fixed-wing aircraft cockpit, comprising:
the mounting port (1) is arranged right above a driver seat in the cockpit;
the shape and the size of the mounting port frame (21) are matched with those of the mounting port (1), and the mounting port frame is detachably and fixedly arranged in the mounting port (1);
the emergency escape window (22) is matched with the mounting opening frame (21) in shape and size and is fixedly arranged in the mounting opening frame (21);
the fixed-wing aircraft cockpit further comprises:
the installation partition plate (3) is fixedly arranged on the inner side of a cockpit top plate right above the seat, the plate surface of the installation partition plate (3) is perpendicular to the cockpit top plate, the installation partition plate (3) is respectively positioned on the left side and the right side of the aircraft course direction, and the left side wall plate and the right side wall plate of the installation port frame (21) in the aircraft course direction are respectively and fixedly connected with the installation partition plate (3) on the corresponding side;
the two sliding rails (41) are symmetrically arranged on the opposite side surfaces of the installation partition plates (3) on the left side and the right side, and the height of the front ends of the sliding rails (41) in the aircraft course direction is greater than that of the rear ends;
the two joints (42) are respectively matched with the slide rails (41), each joint (42) is arranged in one slide rail (41) in a sliding manner, and the two joints (42) are respectively and fixedly connected to the bottoms of the front ends of the mounting port frames (21) on the corresponding sides in the aircraft heading direction;
the two locking handles (43) are symmetrically and rotatably arranged on the opposite side surfaces of the mounting partition plate (3) at the left side and the right side, the rotating axes of the two locking handles are perpendicular to the plate surface of the mounting partition plate (3), and when the locking handle (43) at each side rotates to a preset angle, the locking handle and the sliding rail (41) at the corresponding side can be clamped at the end part of the rear end of the aircraft in the course direction;
operating handle (44), be shaft-like, along the perpendicular to installation baffle (3) face direction is rotated and is set up installation mouthful frame (21) bottom, the axis of rotation perpendicular to of operating handle (44) installation baffle (3) face, and, the both ends of operating handle (44) respectively with correspond the side lock dead handle (43) fixed connection for rotate the drive through self lock dead handle (43) rotate.
2. The fixed-wing aircraft cockpit according to claim 1, characterized in that said mounting bulkhead (3) is also arranged at the front end of said aircraft heading direction and is fixedly connected to the front end wall plate of said mounting port frame (21) in said aircraft heading direction;
the emergency escape window (22) is made of transparent glass;
the fixed-wing aircraft cockpit further includes:
and the reflector (5) is arranged on the mounting partition plate (3) at the front end and used for observing the environment at the top of the cockpit through the emergency escape window.
3. The fixed-wing aircraft cockpit of claim 2, further comprising:
the mounting seat is used for fixedly mounting the reflector (5) on the mounting partition plate (3) and adjusting the observation angle of the reflector (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710645316.XA CN107487434B (en) | 2017-08-01 | 2017-08-01 | Fixed wing aircraft cockpit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710645316.XA CN107487434B (en) | 2017-08-01 | 2017-08-01 | Fixed wing aircraft cockpit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107487434A CN107487434A (en) | 2017-12-19 |
| CN107487434B true CN107487434B (en) | 2020-05-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710645316.XA Active CN107487434B (en) | 2017-08-01 | 2017-08-01 | Fixed wing aircraft cockpit |
Country Status (1)
| Country | Link |
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| CN (1) | CN107487434B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3981685A1 (en) * | 2018-12-07 | 2022-04-13 | Bombardier Inc. | Exterior handle position indicator for aircraft escape hatch |
| CN110127026B (en) * | 2019-04-29 | 2023-11-28 | 中航通飞华南飞机工业有限公司 | Side wind blocking and sliding mechanism for airplane |
| CN111792048B (en) * | 2020-07-22 | 2022-02-18 | 中国商用飞机有限责任公司 | Control device for aircraft cockpit, escape system and cockpit |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2077846A1 (en) * | 1970-02-18 | 1971-11-05 | Dassault Aeronautique | |
| US3847329A (en) * | 1972-08-31 | 1974-11-12 | Stanley Aviation Corp | Rocket escape apparatus |
| FR2696706B1 (en) * | 1992-10-09 | 1994-12-23 | Aerospatiale | Double configuration emergency exit for land evacuation and after landing of an aircraft cabin. |
| DE4338388A1 (en) * | 1993-11-10 | 1995-05-11 | Thomas Matuschak | Emergency escape aid for gliders |
| US5931415A (en) * | 1997-05-09 | 1999-08-03 | The Boeing Company | Plug-type overwing emergency exit door assembly |
| US6208269B1 (en) * | 1999-12-29 | 2001-03-27 | The Boeing Company | Automatically activated rescue radio and associated method |
| US20040159745A1 (en) * | 2003-02-13 | 2004-08-19 | Wood Jeffrey H. | Attachment apparatus for injection-molded frameless canopies |
| US7832686B2 (en) * | 2005-08-23 | 2010-11-16 | Airbus Deutschland Gmbh | Combined displacement and swivel mechanism |
| CN1880168A (en) * | 2005-10-10 | 2006-12-20 | 黄斌 | Self-rescuing passenger plane |
| CN2920717Y (en) * | 2006-05-17 | 2007-07-11 | 张志成 | Hand-operated vehicle dormant window |
| FR2999526A1 (en) * | 2012-12-13 | 2014-06-20 | Airbus Operations Sas | AIRCRAFT COCKPIT EMERGENCY FROM CENTRAL ICE |
| FR3032420B1 (en) * | 2015-02-11 | 2017-01-13 | Airbus Operations Sas | STEERING CABIN FOR AN AIRCRAFT EQUIPPED WITH EMERGENCY EVACUATION |
| CN106335643B (en) * | 2016-10-18 | 2019-02-05 | 刘继军 | Modular ejector seat and escape aircraft comprising it |
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2017
- 2017-08-01 CN CN201710645316.XA patent/CN107487434B/en active Active
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| Publication number | Publication date |
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| CN107487434A (en) | 2017-12-19 |
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